Split combustion liner



May 1, 1962 w. A. TOMOLONIUS SPLIT COMBUSTION LINER 3 Sheets-Sheet 1Filed Aug. 12. 1960 INVENTOR WILL/AM A. TOMOLO/V/US y 1, 1962 w. A.TOMOLONIUS 3,031,844

SPLIT COMBUSTION LINER Filed Aug. 12. 1960 3 Sheets-Sheet 2 INVENTORWILLIAM A. T OMOLON/US gQQZZZ QW AGENTS May 1, 1962 w. A. TOMOLONIUSSPLIT COMBUSTION LINER Filed Aug. 12. 1960 5 Sheets-Sheet s INVENTORWILLIAM A. TOMOLO/V/US GQQ.

AGENTS United States Patent Ofiice 3,031,844 Patented May 1, 19623,031,844 SPLlT CGMBUSTION LINER William A. Tomolonius, North Reading,Mass, assignor, by mesne assignments, to the United States of America asrepresented by the Secretary of the Navy Filed Aug. 12, 1969, er. No.49,490 Ciairns. (Cl. 6G39.69)

The present invention relates to a combustion liner and moreparticularly to a split combustion liner which may readily be removedwithout prior removal of the turbine assembly.

Prior to this invention it has been the practice in the art to make fullannular type combustion liners of a single unitary construction. Suchdesign necessitated the removal of the turbine assembly prior toremoving the old combustion liner when it was necessary to make areplacement or to make a thorough inspection of the condition of thecombustion liner.

The instant invention eliminates the above noted disadvantages by makinga sectional combustion liner. The combustion liner is made in twosections with fastening means for holding the sections in position. Apair of overlapping plates are bolted to the upper and lower portions ofsaid combustion liner to securely hold them in position.

Since combustion liners are subject to high temperatures and thereforeneed to be frequently inspected to determine whether or not replacementis necessary, it can therefore be readily seen that a combustion linerthat could be removed, inspected and/ or replaced without the removal ofthe turbine assembly would be very desirous since a considerable amountof time and money could be saved thereby.

An object of the present invention is the provision of a combustionliner which is easy to manufacture and can be produced at a relativelylow cost.

A further object of the invention is the provision of a split combustionliner which permits inspection and replacement without prior removal ofthe entire turbine assembly.

Still another object of the invention is the provision of a combustionliner which utilizes an overlapping spaced flange for hot regionfastening of parts.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings wherein:

FIG. 1 shows an assembled View of a preferred embodiment of theinvention.

FIG. 2 shows the present invention of FIG. 1 disassembled.

FIG. 3 illustrates the preferred embodiment of the invention with partsremoved.

FIG. 4 is a sectional View taken on the line 4-4 of FIG. 1.

FIG. 5 is a sectional view taken on the line 55 of FIG. 3.

FIG. 6 is a sectional view taken on the line 6-6 of FIG. 3.

Referring now to the drawings, wherein like reference charactersdesignate like or corresponding parts through out the several views,there is shown in FIG. 1 an assembled combustion liner 2 which is formedof two sections, namely, a left-hand section 3 and a right-hand section4. Each section is formed by an inner shell 5 and an outer shell 6 whichare semi-circular in shape and are spaced from each other apredetermined distance by a channel shaped semi-circular member 7. It isthis member 7 that spaces the inner shell 5 and the outer shell 6 thusforming the combustion chamber 21. The channel shaped member 7 isprovided with a plurality of apertures 8 which permit air to enter thespace between the inner shell 5 and the outer shell 6 into thecombustion chamber 21, the inner shell 5 and the outer shell 6 beingfixedly secured to the channel shaped members 7 by welding or some othersuitable means of attachment.

The sections 3 and 4 are each provided with a pair of fastening tabs 9that are secured to the outer face of the channel member 7. Fasteningtabs 9 mate when the sections 3 and 4 are properly aligned and they arethen secured together by holding bolts 11. The manner in which the innerjoint 14 holds the inner shell 5 together will be further explainedbelow.

The outer shell 6 of each section 3 and 4 is provided with a pair ofouter flanges 20. The purpose of the outer flanges 26 is to receive thedome plates 13 which complete the outer shell 6 when fastened togetherby flange bolts 10.

FIG. 2 shows the combustion liner 2 disassembled to better illustratethe manner in which the various components fit together. From this viewit can readily be seen how dome plates 13 of the outer shell 6 overlapthe inner flange 14 of the inner shell 5 and provide access thereto whendome plates 13 are removed.

FIG. 3 is a view similar to FIG. 1 except here the upper dome plate 13has been removed to show the inner joint 14- of the inner shell 5. Theinner joint 14 is fastened together by a plurality of recessed counterhead bolts 15.

FIG. 4 is a sectional view taken along the line 4-4 of FIG. 1. This viewclearly shows the outer joint 12 and the manner in which the flange 20of the dome plates 13 and the flange 20 of the outer shell 6 engage eachother to form the outer joint 12. Once the flanges 20 are properlyaligned, the bolts 10 are inserted through the flanges 2i and thensecured together. This type of flange connection is located at fourplaces, two such flanges 20 holding each dome plate 13 to the outershell 6.

FIG. 5 is a sectional view taken on line 5-5 of FIG. 3 showing themanner in which the inner joint 14 is secured. As shown, the inner shell5 of the right-hand section 4 is overlapped by the inner shell 5 of theleft hand section 3. Both sections 3 and 4 are provided with a pluralityof holes 16 through which recessed counter head bolts 15 are insertedand then fastened by means of nuts 18. The left-hand section 3 of theinner shell 5 is provided with dimples 19 to receive the flat head bolts15.

The use of air pick-up louvers directly in front of dimples 19 andcounter sunk bolt heads15 provide a film of cooling air over the top ofthe bolts and allows this type of holding mechanism to function inextremely hot flame conditions. The overlapping of flanges also picks upair for cooling. In addition to these advantages, the overlap on theinner shell permits less precision to be required in holding toleranceson the sheet metal parts.

As an alternative form, the inner joints 14 and outer joints 12 may bereduced to tabs, or special fasteners with holes or covering sleeves, todirect air for cooling on both outer and inner shells.

FIG. 6 which is a sectional view taken on the line 6-6 of FIG. 3 showsthe combustion chamber 21 and the manner in which the inner shell 5 andthe outer shell 6 combine with the channel shaped member 7 to form thecombustion chamber 21. As pointed out above, the member 7 is providedwith a plurality of apertures 8 which serve as air inlet openings to thecombustion chamber 21. The inner shell 5 and outer shell 6 are alsoprovided with a plurality of openings 22 which permit additional air toenter into combustion chamber 21.

After combustion takes place within chamber 21 the hot gases exit viaoutlet 23 which is of reduced area relative to the cross-sectional areaof chamber 21.

As previously stated above, the instant invention permits the removal ofa full annular type combustion liner from a jet engine without priorremoval of the turbine assembly. The manner in which this isaccomplished is by first removing the outer combustion casing of the jetengine (not shown). After this is done, the combustion liner outer shell6 is exposed. Then the flange bolts 10 are removed, permitting the domeplates 13 to be removed. Upon removing dome plates 13, the inner joint14 isexposed and the recessed bolts 15 are then removed. After this isdone, the holding bolts 11 are removed thus splitting the annularcombustion liner into two sections, sections 3 and 4.

It is to be noted that only the upper-half of the liner has beenunfastened, however, and it is to be understood that the same steps areto be taken on the lower-half of the liner also.

After the upper and lower halves have been unfastened, then the sectionsmay be rotated and manipulated in such a manner as to permit the linerto be removed in two sections without prior removal of the turbineassembly.

Obviously many modifications and variations of the present invention arepossible in the light of the above teachings. It is therefore to beunderstood that Within the scope of the appended claims, the inventionmay be practiced otherwise than as specifically described.

What is claimed is:

1. In an engine having a turbine assembly, a compressor assembly, anannular combustion liner having spaced perforate inner and outer shellsforming a combustion chamber therebetween, the improvement in saidannular combustion liner comprising a first and second semi-cylindricalsection, each of said sections having an inner and outer shell, saidouter shells having a flange at each end and extending over a lesserdegree of arc than said inner shells, said flanges having holes thereinfor receiving fastening bolts, a pair of dome plates having a flange ateach end, said flanges having holes therein permitting said dome platesto be fastened to said outer shells to complete said outer shell, innerjoint means for releasably fastening said inner shells of said first andsecond sections, means for cooling said inner joint means, said flangeson said outer shells and said dome plates cooperating to form the outerjoint means for releasably fastening said dome plates to said outershells of said first and second sections, said dome plates being ofsufficient width to provide access to said inner joint means wherebysaid first and second sections may be readily removed from an enginewithout prior removal of said turbine assembly.

2. In an engine having a turbine assembly, a compressor assembly, anannular combustion liner having spaced perforate inner and outer shellsforming a combustion chamber therebetween, the improvement in saidannular combustion liner comprising a first and second semi-cylindricalsection, each of said sections having a perforate inner and outer shell,said outer shells having a flange at each end and extending over alesser degree of arc than said inner shells, said flanges having holestherein for receiving fastening bolts, a pair of dome plates, said domeplates having a flange at each end, said flanges having holes thereinpermitting said dome plates to be fastened to said outer shells tocomplete said outer shell a pair of semi-circular channel shaped membershaving apertures therein spacing said inner and outer shells apredetermined distance, said shells being fixedly secured at one end tosaid channel shaped members, inner joint means for releasably fasteningsaid inner shells of said first and second sections, means for coolingsaid inner joint means, said flanges on said outer shells and said domeplates cooperating to form the outer joint means for releasablyfastening said dome plates to said outer shells of said first and secondsections, said dome plates being of sufiicient width to provide accessto said inner joint means whereby said first and second sections may bereadily removed from an engine without prior removal of said turbineassembly.

3. In a device as described in claim 2 wherein said inner joint meansfor releasably fastening said inner shells of said first and secondsections is formed by said inner shell of said first section overlappingsaid inner shell of said second section, the overlapping portions ofsaid shells having a plurality of aligned apertures for receivingfastening bolts.

4. In a device as described in claim 3 wherein said means for coolingsaid inner joint means is formed by said first section overlapping saidsecond section in such a manner as to scoop up air passing therethroughwhereby this type of joint means can function properly in extremely hotflame regions.

5. In a device as described in claim 2 wherein said means for coolingsaid inner joint means is formed by said first section overlapping saidsecond section in such a manner as to scoop up air passing therethroughwhereby this type of joint means can function in extremely hot flameregions.

References Cited in the file of this patent UNITED STATES PATENTS 58,648Joy Oct. 9, 1866 2,537,054 Hildestad Jan. 9, 1951 2,645,081 McDonaldJuly 14, 1953 2,760,338 Keast Aug. 28, 1956 2,988,886 Hamm June 20, 1961

